NAA engineers began preliminary layouts to define the elements of the command module (CM) configuration. Additional requirements and limitations imposed on the CM included reduction in diameter, paraglider compatibility, 250 pounds of radiation protection water, redundant propellant tankage for the attitude control system, and an increase in system weight and volume.

Layouts were also being prepared to identify equipment requirements in the CM aft compartment, while layouts depicting the position and orientation of the three crewmen during various phases of the lunar flight were complete.

Basic load paths for the CM inner structure, an access door through the outer structure, and the three side wall hatches for crew entrance and exit had been tentatively defined. The CM inner structure was currently of bonded aluminum honeycomb, the outer structure of high-temperature, brazed steel honeycomb.
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